Use of Zig-zag Theory in Finite Element Formulation for Analysis of Composite Plates

摘要

This paper deals with the application of a first-order zig-zag theory that accounts for realistic variation of in-plane displacements through thickness in a thick multi-layered composite plate for dynamic response analysis. The solutions of dynamic equations are obtained by employing the finite element procedure, based on a C~0 continuous, four-node isoparametric element with seven degrees of freedom at each node. A zig-zag shaped C~0 function is used for modelling the in-plane displacements through the thickness oj the laminates. The comparison of in-plane response with exact solutions for symmetric cross ply laminate demonstrates that the present theory predicts the in-plane rtsponse very accurately, even for small span to depth ratios. The effects of aspect ratio, numbers of layers, and lamination scheme on the dynamic response of composite laminate are investigated.